CA2600198A1 - Component, in particular, a gas turbine component - Google Patents
Component, in particular, a gas turbine component Download PDFInfo
- Publication number
- CA2600198A1 CA2600198A1 CA002600198A CA2600198A CA2600198A1 CA 2600198 A1 CA2600198 A1 CA 2600198A1 CA 002600198 A CA002600198 A CA 002600198A CA 2600198 A CA2600198 A CA 2600198A CA 2600198 A1 CA2600198 A1 CA 2600198A1
- Authority
- CA
- Canada
- Prior art keywords
- gas turbine
- main body
- component
- barrier coat
- turbine component
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
- C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
- C23C28/023—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material only coatings of metal elements only
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0466—Nickel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/131—Molybdenum
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
- F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a component, in particular a gas turbine component, comprising a base body (11) which is made of a base material and of a wear-and-tear protective coating (12) which is applied to the surface of the base body (11), in particular, a coating which protects against corrosion and/or oxidation and/or erosion. According to the invention, a blocking layer (16) is positioned between the base body (11) and the wear-and tear coating (12) in order to protect the base body (11) during a chemical or electrochemical removal of a coating of the component (10).
Description
Component, Specifically A Component For A Gas Turbine The invention relates to a component, specifically a component for a gas turbine in accordance with the preamble of claim 1.
Components for a gas turbine, such as the rotor blades, are given special wear protection coatings to provide oxidation resistance, corrosion resistance or erosion resistance. The components of gas turbines are subject to wear during operation or can be damaged in other ways. To repair damage it is usually necessary to remove or strip the wear protection coating from the component to be repaired in specific areas, partially or even completely. The removal or stripping of coatings is also called decoating. In the decoating processes a distinction is made between those in which the decoating is carried out by mechanical means, chemical means or electrochemical means.
With chemical or even electrochemical decoating of a component the risk exists that the basic material of the main body coated with the wear-protection coating will be attacked or removed. With some base materials, such as titanium alloys, this can result in a deterioration of the material properties. In the case of titanium alloys the HCF strength may be reduced.
Consequently, in accordance with the prior art, expensive steps must be taken in the decoating of components to prevent the basic material of the main body from being attacked.
With this as the starting point, the problem underlying the present invention is to create a novel component, specifically a novel component for a gas turbine.
This problem is solved by a component, specifically a component for a gas turbine, in accordance with claim 1. In accordance with the invention, a resistive layer is located between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component.
Within the meaning of the present invention it is proposed to locate a resistive layer between the main body and the wear protection coating for a coated component. The protection coating protects the main body of the component from attack from the decoating during chemical or electrochemical decoating. To this extent, there is no further risk during chemical or electrochemical decoating of such a component that the material properties of the base material are negatively affected. The protection coating is resistant to chemical and electrochemical decoating.
Preferably the barrier coating has a material composition matched to the material composition of the main body, where the material of the barrier coating is alloyed, or enriched with an element relative to the base material of the main body from the platinum group and/or with nickel andlor with molybdenum.
Preferred further developments of the invention emerge from the dependent claims and the subsequent description. An embodiment of the invention, without being limited thereto, is described in more detail using the drawing.
Fig. 1 shows a schematic cross-section through the component in accordance with the invention.
Hereinafter the invention is described in greater detail with reference to Fig.
1.
Fig. 1 shows a schematic cross-section through a component 10 in accordance with the invention, where the component 10 consists of a main body 11 and a wear protection coating 12 applied to a surface of the main body 11. In the embodiment shown the wear protection coating 12 is a multi-layer, or multi-coat, wear protection coating 12 consisting of layers 13, 14, and 15. The layers 13, 14, and 15 of the wear protection coating may be alternately relatively hard or relatively soft layers, or coats. There can be any number of layers in the wear protection coating 12 and this is of subordinate importance for the present invention.
Within the meaning of the present invention, a barrier coat 16 is positioned between the wear protection coating 12 and the main body 11 of the component 10 in accordance with the invention. The barrier coat 16 is located between the main body 11 and the lowest, or innermost, layer 13 of the wear protection coating 12. The barrier coat 16 assumes the function of protecting the main body 11 during chemical or electrochemical decoating.
The barrier coat 16 is therefore resistant to chemical or electrochemical decoating and is not attacked, or removed, during such a decoating so that the base material of the main body 11 is not attacked or removed.
The barrier coat 16 has a material composition which is matched to the material composition of the main body 11. Preferably both the main body 11 as well as the barrier coat 16 are made from a titanium-based alloy. The material of the barrier coat 16 is enriched or alloyed with at least one element from the platinum group and/or with nickel andJor molybdenum relative to the base material of the main body 11.
Thus the material of the barrier coat 16 may have platinum in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have palladium in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have nickel in a percentage of at least 0.50% by weight and/or molybdenum in a percentage of at least 4.00 % by weight. One or even more of these elements may be present in the above specified proportions in the barrier coat 16.
As already mentioned, the barrier coat protects the base material of the main body against attack during chemical or electrochemical decoating of the component. This ensures that during decoating the material properties of the base material of the main body are not negatively affected. An additional advantage of the barrier coat is that it is relatively smooth. Thus, following decoating a newly applied wear protection coating is able to adhere better to the base body than would have been possible with decoating in the case of a main body attacked or etched during decoating from the state of the art.
Since the barrier coat has a material composition matched to the material composition of the main body there are no matching problems for the wear protection coating.
Components for a gas turbine, such as the rotor blades, are given special wear protection coatings to provide oxidation resistance, corrosion resistance or erosion resistance. The components of gas turbines are subject to wear during operation or can be damaged in other ways. To repair damage it is usually necessary to remove or strip the wear protection coating from the component to be repaired in specific areas, partially or even completely. The removal or stripping of coatings is also called decoating. In the decoating processes a distinction is made between those in which the decoating is carried out by mechanical means, chemical means or electrochemical means.
With chemical or even electrochemical decoating of a component the risk exists that the basic material of the main body coated with the wear-protection coating will be attacked or removed. With some base materials, such as titanium alloys, this can result in a deterioration of the material properties. In the case of titanium alloys the HCF strength may be reduced.
Consequently, in accordance with the prior art, expensive steps must be taken in the decoating of components to prevent the basic material of the main body from being attacked.
With this as the starting point, the problem underlying the present invention is to create a novel component, specifically a novel component for a gas turbine.
This problem is solved by a component, specifically a component for a gas turbine, in accordance with claim 1. In accordance with the invention, a resistive layer is located between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component.
Within the meaning of the present invention it is proposed to locate a resistive layer between the main body and the wear protection coating for a coated component. The protection coating protects the main body of the component from attack from the decoating during chemical or electrochemical decoating. To this extent, there is no further risk during chemical or electrochemical decoating of such a component that the material properties of the base material are negatively affected. The protection coating is resistant to chemical and electrochemical decoating.
Preferably the barrier coating has a material composition matched to the material composition of the main body, where the material of the barrier coating is alloyed, or enriched with an element relative to the base material of the main body from the platinum group and/or with nickel andlor with molybdenum.
Preferred further developments of the invention emerge from the dependent claims and the subsequent description. An embodiment of the invention, without being limited thereto, is described in more detail using the drawing.
Fig. 1 shows a schematic cross-section through the component in accordance with the invention.
Hereinafter the invention is described in greater detail with reference to Fig.
1.
Fig. 1 shows a schematic cross-section through a component 10 in accordance with the invention, where the component 10 consists of a main body 11 and a wear protection coating 12 applied to a surface of the main body 11. In the embodiment shown the wear protection coating 12 is a multi-layer, or multi-coat, wear protection coating 12 consisting of layers 13, 14, and 15. The layers 13, 14, and 15 of the wear protection coating may be alternately relatively hard or relatively soft layers, or coats. There can be any number of layers in the wear protection coating 12 and this is of subordinate importance for the present invention.
Within the meaning of the present invention, a barrier coat 16 is positioned between the wear protection coating 12 and the main body 11 of the component 10 in accordance with the invention. The barrier coat 16 is located between the main body 11 and the lowest, or innermost, layer 13 of the wear protection coating 12. The barrier coat 16 assumes the function of protecting the main body 11 during chemical or electrochemical decoating.
The barrier coat 16 is therefore resistant to chemical or electrochemical decoating and is not attacked, or removed, during such a decoating so that the base material of the main body 11 is not attacked or removed.
The barrier coat 16 has a material composition which is matched to the material composition of the main body 11. Preferably both the main body 11 as well as the barrier coat 16 are made from a titanium-based alloy. The material of the barrier coat 16 is enriched or alloyed with at least one element from the platinum group and/or with nickel andJor molybdenum relative to the base material of the main body 11.
Thus the material of the barrier coat 16 may have platinum in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have palladium in a percentage of at least 0.05% by weight. Similarly, the material of the barrier coat 16 may have nickel in a percentage of at least 0.50% by weight and/or molybdenum in a percentage of at least 4.00 % by weight. One or even more of these elements may be present in the above specified proportions in the barrier coat 16.
As already mentioned, the barrier coat protects the base material of the main body against attack during chemical or electrochemical decoating of the component. This ensures that during decoating the material properties of the base material of the main body are not negatively affected. An additional advantage of the barrier coat is that it is relatively smooth. Thus, following decoating a newly applied wear protection coating is able to adhere better to the base body than would have been possible with decoating in the case of a main body attacked or etched during decoating from the state of the art.
Since the barrier coat has a material composition matched to the material composition of the main body there are no matching problems for the wear protection coating.
Claims (8)
1. ~Gas turbine component, having a main body (11) made of a base material and a wear protection coating (12) against corrosion and/or oxidation and/or erosion applied to a surface of the main body (11) and a barrier coat (16) applied between the main body (11) and the wear protection coating (12) characterized in that the barrier (16) is configured with a relatively smooth surface and is resistant to chemical or electrochemical decoating and wherein the wear protection coating (12) is multi-layered.
2. ~Gas turbine component from claim 1, wherein the barrier coat (16) has a material composition matching the material composition of the main body (11).
3. ~Gas turbine component from claim 1 or 2, wherein the material of the barrier coat (16), compared with the base material of the main body (11) is enriched or alloyed with at least one element from the platinum group and/or with nickel and/or with molybdenum.
4. ~Gas turbine component from claim 3, wherein the material of the barrier coat (16) contains platinum in the amount of at least 0.05%
by weight.
by weight.
5. ~Gas turbine component from claim 3 or 4, wherein the material of the barrier coat (16) contains palladium in an amount of at least 0.05% by weight.
6. ~Gas turbine component from one or more of the claims 3 to 5, wherein the material of the barrier coat (16) contains nickel in an amount of at least 0.50% by weight.
7. ~Gas turbine component from one or more of the claims 3 to 6, wherein the material of the barrier coat (16) contains molybdenum in an amount of at least 4.00% by weight.
8. Gas turbine component from one or more of the claims 1 to 7, wherein the base material of the main body and the material of the barrier coat (16) are titanium alloys.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005011011A DE102005011011A1 (en) | 2005-03-10 | 2005-03-10 | Component, in particular gas turbine component |
DE102005011011.8 | 2005-03-10 | ||
PCT/DE2006/000379 WO2006094481A1 (en) | 2005-03-10 | 2006-03-03 | Component, in particular, a gas turbine component |
Publications (1)
Publication Number | Publication Date |
---|---|
CA2600198A1 true CA2600198A1 (en) | 2006-09-14 |
Family
ID=36646061
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CA002600198A Abandoned CA2600198A1 (en) | 2005-03-10 | 2006-03-03 | Component, in particular, a gas turbine component |
Country Status (5)
Country | Link |
---|---|
US (1) | US20090269207A1 (en) |
EP (1) | EP1856306A1 (en) |
CA (1) | CA2600198A1 (en) |
DE (1) | DE102005011011A1 (en) |
WO (1) | WO2006094481A1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2566697C2 (en) | 2011-04-13 | 2015-10-27 | Роллс-Ройс Корпорейшн | Interfacial diffusion barrier layer including iridium on metallic substrate |
EP2918705B1 (en) | 2014-03-12 | 2017-05-03 | Rolls-Royce Corporation | Coating including diffusion barrier layer including iridium and oxide layer and method of coating |
DE102015208781A1 (en) * | 2015-05-12 | 2016-11-17 | MTU Aero Engines AG | Combination of blade tip armor and erosion control layer and method of making the same |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4761346A (en) * | 1984-11-19 | 1988-08-02 | Avco Corporation | Erosion-resistant coating system |
WO1991002108A1 (en) * | 1989-08-10 | 1991-02-21 | Siemens Aktiengesellschaft | High-temperature-resistant, corrosion-resistant coating, in particular for components of gas turbines |
US6071627A (en) * | 1996-03-29 | 2000-06-06 | Kabushiki Kaisha Toshiba | Heat-resistant member and a method for evaluating quality of a heat-resistant member |
EP0872575A2 (en) * | 1997-04-19 | 1998-10-21 | Institut für Festkörper- und Werkstofforschung Dresden e.V. | Protective surface coating for titanium alloys |
US6830827B2 (en) * | 2000-03-07 | 2004-12-14 | Ebara Corporation | Alloy coating, method for forming the same, and member for high temperature apparatuses |
US6475642B1 (en) * | 2000-08-31 | 2002-11-05 | General Electric Company | Oxidation-resistant coatings, and related articles and processes |
US6620525B1 (en) * | 2000-11-09 | 2003-09-16 | General Electric Company | Thermal barrier coating with improved erosion and impact resistance and process therefor |
DE10210518A1 (en) * | 2002-03-09 | 2003-10-02 | Mtu Aero Engines Gmbh | Process for stripping engine components and device for carrying out the process |
US6969457B2 (en) * | 2002-10-21 | 2005-11-29 | General Electric Company | Method for partially stripping a coating from the surface of a substrate, and related articles and compositions |
DE102004001722A1 (en) * | 2004-01-13 | 2005-08-04 | Mtu Aero Engines Gmbh | Turbomachine blade and method of making blade tip armor on turbomachinery blades |
US20090176110A1 (en) * | 2008-01-08 | 2009-07-09 | General Electric Company | Erosion and corrosion-resistant coating system and process therefor |
-
2005
- 2005-03-10 DE DE102005011011A patent/DE102005011011A1/en not_active Withdrawn
-
2006
- 2006-03-03 US US11/908,092 patent/US20090269207A1/en not_active Abandoned
- 2006-03-03 EP EP06722548A patent/EP1856306A1/en not_active Withdrawn
- 2006-03-03 CA CA002600198A patent/CA2600198A1/en not_active Abandoned
- 2006-03-03 WO PCT/DE2006/000379 patent/WO2006094481A1/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
US20090269207A1 (en) | 2009-10-29 |
WO2006094481A1 (en) | 2006-09-14 |
DE102005011011A1 (en) | 2006-09-14 |
EP1856306A1 (en) | 2007-11-21 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
EEER | Examination request | ||
FZDE | Discontinued |
Effective date: 20130304 |